JP4460795B2 - Thruster device - Google Patents

Description

【００３２】
ただし、ζ：圧力損失係数、ｇ：重力加速度、γ：密度、ｖ：流速、ｗ：流量Ａ：噴射断面積である。
【００３３】
前記大径ノズル２５，３５と小径ノズル２６，３６とは、それぞれの流路断面積が、前記式１にしたがって、大推力モードの時に噴射する流量の燃料及び酸化剤の圧力と、小推力モードの時に噴射する流量の燃料及び酸化剤の圧力とが、互いに等しくなるように形成されている。
【００３４】
本実施形態によれば、スラスタ装置１と噴射方向が同軸に配された姿勢変更用のスラスタを省略しても、スラスタ装置１を小推力モードで駆動することによって、姿勢変更を行う際に用いることが可能となる。したがって、部品点数を抑制することが可能となる。
【００３５】
また、前記スラスタ装置１は、大推力モードでは大径ノズル２５，３５及び小径ノズル２６，３６双方を用い、小推力モードでは小径ノズル２６，３６のみを用いるとともに、大径ノズル２５，３５及び小径ノズル２６，３６の流路断面積が、大推力モードの時に噴射する燃料及び酸化剤の圧力と小推力モードの時に噴射する燃料及び酸化剤の圧力とが等しくなるように形成されているので、小推力モードの際に燃料と酸化剤の流量を抑制してもこれらの燃料と酸化剤の圧力が低下することがない。したがって、小推力モードにおいても常に安定した燃焼を行うことが可能となる。
【００３６】
図２は、第２の実施形態を示し、前述した第１の実施形態と同一構成部分には、同一符号を付して説明を省略する。
【００３７】
本実施形態のスラスタ装置１は、推力変更部材３が、断面形状が上方に開口したコ字形に形成されている。推力変更部材３の外周面１２ａと装置本体２の周壁８の内周面１３ａとの間のシール部材１７が、推力変更部材３の全長に亘って、これらの外周面１２ａと内周面１３ａとの間を流体密に保つように配されている。
【００３８】
このため、本実施形態のスラスタ装置１は、推力変更部材３が冷却路としての冷却管部４１を備えている。図示例において、この冷却管部４１は、一端部４１ａが燃料供給手段５の燃料マニホールド２１の枝管部２４に開口しているとともに、他端部４１ｂがノズル４内の通路１８に開口している。
【００３９】
前述した構成のスラスタ装置１は、燃料供給手段５の燃料マニホールド２１の枝管部２４から冷却管部４１を通って、ノズル４内に供給される燃料が、ノズル４の熱によって気化される。この気化する際の潜熱によって、ノズル４が冷却されることとなる。
【００４０】
本実施形態のスラスタ装置１は、第１の実施形態と同様に、部品点数を抑制できるとともに、小推力モードにおいても常に安定した燃焼を行うことが可能となる。
【００４１】
また、図示した本実施形態のスラスタ装置１は、冷却管部４１が、燃料供給手段５の燃料マニホールド２１の枝管部２４に開口しているが、酸化剤供給手段６の酸化剤マニホールド３１の枝管部３４に開口するように冷却管部４１を形成しても良い。
【００４２】
【発明の効果】
本発明のスラスタ装置によれば、比較的流路断面積が大きな大径ノズルと、比較的流路断面積が小さな小径ノズルと、を備え、大径及び小径ノズルの双方を用いて噴射ノズル内に燃料と酸化剤とを供給する大推力モードと、小径ノズルのみを用いて噴射ノズル内に燃料と酸化剤とを供給する小推力モードと、が切り換え可能となっている。
【００４３】
このため、前記スラスタ装置を小推力モードで駆動することによって、このスラスタ装置と噴射方向が同軸に配された姿勢制御用のスラスタを省略しても、本発明のスラスタ装置を姿勢制御に用いることが可能となる。したがって、部品点数を抑制することが可能となる。
【００４４】
また、前記スラスタ装置は、大推力モードでは大径及び小径ノズル双方を用い、小推力モードでは小径ノズルのみを用いるので、姿勢制御する際に燃料と酸化剤の流量を抑制してもこれらの燃料と酸化剤の圧力が低下することがない。したがって、小推力モードにおいても常に安定した燃焼を行うことが可能となる。
【図面の簡単な説明】
【図１】本発明の第１の実施形態のスラスタ装置を示す断面図。
【図２】図１中のｉｉ−ｉｉ線に沿う断面図。
【図３】この発明の第２の実施形態のスラスタ装置を示す断面図。
【図４】従来のスラスタ装置の構成を示す概念図。
【符号の説明】
１…スラスタ装置
２…装置本体
３…推力変更部材（推力変更手段）
４…ノズル
５…燃料供給手段
６…酸化剤供給手段
１７…シール部材（シール手段）
２５…燃料大径ノズル（大径ノズル）
２６…燃料小径ノズル（小径ノズル）
３５…酸化剤大径ノズル（大径ノズル）
３６…酸化剤小径ノズル（小径ノズル）
４１…冷却管部（冷却路）[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a thruster device used in a spacecraft, an artificial satellite, and the like.
[0002]
[Prior art]
For example, a thruster device 51 shown in FIG. 4 may be used for a spacecraft or an artificial satellite.
[0003]
The thruster device 51 illustrated in FIG. 4 includes, for example, a plurality of large thrusters 52 used when changing the trajectory, a plurality of small thrusters 53 used when assisting or changing the attitude of the large thruster 52, and a fuel supply. Means 54 and oxidant supply means 55 are provided.
[0004]
The large thrusters 52 are arranged so that the injection directions are coaxial with each other. The large thruster 52 is supplied with a relatively large flow of fuel from the fuel supply means 54 and a relatively large flow of oxidant from the oxidant supply means 55. The large thruster 52 collides with a relatively large flow rate of fuel and oxidant and burns to generate a relatively large propulsive force.
[0005]
The plurality of small thrusters 53 include those in which the large thrusters 52 and the injection directions are arranged coaxially with each other, and those in which the injection directions intersect with the injection directions of the large thrusters 52. Each small thruster 53 is supplied with a relatively small flow rate of fuel from the fuel supply means 54 and a relatively small flow rate of oxidant from the oxidant supply means 55. The small thruster 53 collides with a relatively small flow rate of fuel and oxidant and burns with each other to generate a relatively small thrust.
[0006]
[Problems to be solved by the invention]
However, since the conventional thruster 51 described above includes the large thruster 52 and the plurality of small thrusters 53, the number of parts tends to increase and the cost tends to increase. Further, the small thruster 53 whose injection direction is coaxially arranged with the large thruster 52 is omitted, and the flow of fuel and oxidant supplied to the large thruster 52 is suppressed to obtain a relatively small thrust, and the large thruster 52 is If it is intended to be used when the posture is changed, the pressure of the injected fuel and oxidant is lowered, and it is difficult to ignite and the combustion may become unstable.
[0007]
Accordingly, an object of the present invention is to provide a thruster device that can suppress the increase in cost by suppressing the number of parts and can always perform stable combustion.
[0008]
[Means for Solving the Problems]
In order to solve the above-mentioned problems and achieve the object, a thruster device according to claim 1 is provided with a device main body that is connected to a nozzle and forms an outer shell of the device, and a fuel that is attached to the device main body and that supplies fuel into the nozzle. A thruster apparatus comprising: a fuel supply means for supplying; and an oxidant supply means attached to the apparatus main body and supplying an oxidant into the nozzle. The fuel supplied from the fuel supply means is supplied into the nozzle. A large-diameter fuel nozzle with a relatively large cross-sectional area for guiding, a small-diameter fuel nozzle with a relatively small cross-sectional area for the flow path, and a relatively small flow path disconnection for guiding the oxidant supplied from the oxidant supply means into the nozzle. a large oxidant large nozzle area, a small oxidizer diameter nozzle is relatively channel cross-sectional area, comprising a, and whether the fuel supply means and the oxidizer supply means with said large-diameter nozzle and small diameter nozzle A large thrust mode for guiding each of the supplied fuel and oxidant into the nozzle, and a small thrust for guiding each of the fuel and oxidant supplied from the fuel supply means and oxidant supply means into the nozzle using only the small diameter nozzle. A thrust change member provided so as to be switchable by rotating the mode with respect to the apparatus main body, and a drive source for rotating the thrust change member .
[0009]
A thruster device according to a second aspect is the thruster device according to the first aspect, wherein the thrust changing member is formed in a U-shaped cross section and is supplied from the fuel supply means between the device main body and the thruster device. Seal means for preventing leakage of at least one of the fuel and the oxidant supplied from the oxidant supply means, and the large diameter nozzle and the small diameter nozzle are separate from each other and at least one of the fuel and the oxidant And a cooling path for guiding the gas into the nozzle.
[0010]
DETAILED DESCRIPTION OF THE INVENTION
A first embodiment of the present invention will be described below with reference to FIGS. 1 and 2.
[0011]
A thruster apparatus 1 shown in FIG. 1 is used for a spacecraft, an artificial satellite, and the like, and is used when the spacecraft, an artificial satellite changes its orbit or changes its attitude. The thruster device 1 uses, for example, dinitrogen tetroxide (hereinafter referred to as NTO) that burns when in contact with each other as an oxidizing agent and monomethylhydrazine (hereinafter referred to as MMH) as a fuel.
[0012]
As shown in FIG. 1, the thruster device 1 includes a device main body 2 that forms an outline of the device, a thrust changing member 3 as a thrust changing means that is rotatably provided in the device main body 2, and a device main body 2. The nozzle 4 connected to this, the fuel supply means 5, and the oxidizing agent supply means 6 are provided.
[0013]
The apparatus main body 2 is formed in an inverted bottomed cylindrical shape, and integrally includes a bottom portion 7 located on the upper side in the figure and a peripheral wall 8 extending downward from the peripheral edge of the bottom portion 7 in the figure. Yes. The apparatus main body 2 is integrally provided with a cylindrical portion 9 extending from the center of the bottom portion 7 together with the peripheral wall 8 downward in the figure.
[0014]
The thrust changing member 3 is formed in an annular shape, and is provided in the apparatus main body 2 in a state where the cylindrical portion 9 of the apparatus main body 2 passes through a through hole 10 provided in the center. The thrust changing member 3 is rotatably supported in the apparatus main body 2 by a bearing 11. The thrust changing member 3 has an outer peripheral surface 12 a in close contact with the inner peripheral surface 13 a of the peripheral wall 8 of the apparatus main body 2, and an inner peripheral surface 12 b in close contact with the outer peripheral surface 13 b of the cylindrical portion 9 of the apparatus main body 4. ing.
[0015]
The thrust changing member 3 is provided with external teeth 14 along the circumferential direction on the outer peripheral surface 12a. A gear 16 that is rotationally driven by a drive source 15 meshes with the external teeth 14. In addition, a plurality of sealing members 17 are provided between the apparatus main body 2 and the thrust change member 3 as sealing means for keeping fluid tightness between each other.
[0016]
The nozzle 4 is formed in a cylindrical shape, and one end 4 a is connected to the end 8 a of the peripheral wall 8 of the apparatus main body 2. Inside the nozzle 4, a passage 18 is formed through which fumes generated when the fuel and the oxidant are burned pass.
[0017]
The fuel supply means 5 is attached to the apparatus main body 2 and includes a fuel manifold 21 to which fuel is supplied from a fuel supply source (not shown), a fuel injection nozzle 22 formed in the thrust changing member 3, and the like. . The fuel manifold 21 includes a merging pipe portion 23 connected to a fuel supply source, and a plurality of branch pipe portions 24 branched from the merging pipe portion 23.
[0018]
The fuel injection nozzles 22 are provided in the same number as the branch pipe portions 24 of the fuel manifold 21, and one end portion 22 a is open to the branch pipe portion 24 of the fuel manifold 21 and the other end portion 22 b is the nozzle 4. It opens to the inner passage 18.
[0019]
As shown in FIG. 2, the fuel injection nozzle 22 includes a fuel large-diameter nozzle 25 having a relatively large flow path cross-sectional area and a fuel small-diameter nozzle 26 having a relatively small flow path cross-sectional area. With the above-described configuration, the fuel supply means 5 is supplied with fuel at a predetermined pressure from a fuel supply source (not shown), and guides and injects the fuel into the nozzle 4 via the fuel manifold 21 and the fuel injection nozzle 22.
[0020]
The oxidant supply means 6 is attached to the apparatus main body 2, and an oxidant manifold 31 to which an oxidant is supplied from an oxidant supply source (not shown) and an oxidant injection nozzle 32 formed in the thrust changing member 3. Etc. The oxidant manifold 31 includes a merging pipe part 33 connected to an oxidant supply source and a plurality of branch pipe parts 34 branched from the merging pipe part 33.
[0021]
The oxidant injection nozzles 32 are provided in the same number as the branch pipe portions 34 of the oxidant manifold 31. One end portion 32 a is open to the branch pipe portion 34 of the oxidant manifold 31 and the other end portion 32 b is provided. It opens to the passage 18 in the nozzle 4.
[0022]
Similar to the fuel injection nozzle 22, the oxidant injection nozzle 32 includes an oxidant large-diameter nozzle 35 having a relatively large channel cross-sectional area and an oxidant small-diameter nozzle 36 having a relatively small channel cross-sectional area. . With the configuration described above, the oxidant supply means 6 is supplied with an oxidant having a predetermined pressure from an oxidant supply source (not shown), and guides the oxidant into the nozzle 4 through the oxidant manifold 31 and the oxidant injection nozzle 32. Spray.
[0023]
The fuel large-diameter nozzle 25 and the oxidant large-diameter nozzle 35 are large-diameter nozzles described in this specification. The fuel small diameter nozzle 26 and the oxidant small diameter nozzle 36 are the small diameter nozzles described in this specification.
[0024]
In addition, the other end portion 22b opened in the nozzle 4 of the fuel injection nozzle 22 and the other end portion 32b opened in the nozzle 4 of the oxidant injection nozzle 32 have fuel and oxidant injected into the nozzle 4 inside each other. The passage 18 is formed so as to collide.
[0025]
Sealing member 1 7 described above, the fuel and the nozzle 4 side from the respective branch pipe part 24, 34 of the fuel and oxidant manifold 21 and 31 of the oxidant supplying means 5 and 6 is not provided. For this reason, the fuel and the oxidant are separated from the inner peripheral surface 13a of the peripheral wall 8 of the apparatus main body 4 and the outer peripheral surface 12a of the thrust changing member 3 from the branch pipe portions 24 and 34 of the manifolds 21 and 31, respectively, by capillary action. And, it will ooze out into the nozzle 4 from between the outer peripheral surface 13b of the cylindrical portion 9 of the apparatus main body 2 and the inner peripheral surface 12b of the thrust changing member 3.
[0026]
For this reason, after the fuel and the oxidant collide with each other in the nozzle 4 to make the fuel, the fuel and the oxidant exuded as described above are vaporized by the heat of the thruster 1, particularly the nozzle 4. It will be. And it will cool by the latent heat at the time of the nozzle 4 evaporating.
[0027]
According to the configuration described above, the thruster device 1 rotates the thrust changing member 3 with the driving source 15 when changing the orbit of the spacecraft or the artificial satellite, as shown in FIG. The fuel supply means 5 and the oxidant supply means 6 guide the fuel and the oxidant into the nozzle 4 using the large diameter nozzles 25 and 35 and the small diameters 26 and 36 to generate a relatively large thrust.
[0028]
Further, the thruster device 1 rotates the thrust changing member 3 by the drive source 15 when changing the orbit of the spacecraft or the artificial satellite, as shown in FIG. The oxidant supply means 6 guides the fuel and the oxidant into the nozzle 4 using only the small diameter nozzles 26 and 36, and generates a relatively small thrust.
[0029]
As described above, the thruster device 1 uses the large-diameter nozzles 25 and 35 and the small-diameter nozzles 26 and 36 to supply the fuel and the oxidant supplied from the fuel supply unit 5 and the oxidant supply unit 6 into the nozzle 4. The large thrust mode for guiding and the small thrust mode for guiding the fuel and the oxidant supplied from the fuel supply means 5 and the oxidant supply means 6 into the nozzle 4 using only the small diameter nozzles 26 and 36 can be switched. ing.
[0030]
In general, it is known that the pressure P of the fluid ejected from the nozzle satisfies the following formula 1.
[0031]
[Expression 1]

[0032]
Where ζ: pressure loss coefficient, g: gravitational acceleration, γ: density, v: flow velocity, w: flow rate A: injection cross section.
[0033]
The large-diameter nozzles 25 and 35 and the small-diameter nozzles 26 and 36 have the flow path cross-sectional areas of the fuel and oxidant pressures injected when the large thrust mode and the small thrust mode, respectively, according to the above equation 1. At this time, the flow rate of fuel and the pressure of the oxidant injected are set to be equal to each other.
[0034]
According to the present embodiment, even if the thruster for posture change whose injection direction is arranged coaxially with the thruster device 1 is omitted, the thruster device 1 is used for changing the posture by driving in the small thrust mode. It becomes possible. Therefore, the number of parts can be suppressed.
[0035]
The thruster device 1 uses both the large diameter nozzles 25 and 35 and the small diameter nozzles 26 and 36 in the large thrust mode, and uses only the small diameter nozzles 26 and 36 in the small thrust mode, and also uses the large diameter nozzles 25 and 35 and the small diameter nozzles. Since the flow path cross-sectional area of the nozzles 26 and 36 is formed so that the pressure of the fuel and oxidant injected in the large thrust mode is equal to the pressure of the fuel and oxidant injected in the small thrust mode. Even if the flow rates of the fuel and the oxidant are suppressed in the small thrust mode, the pressure of the fuel and the oxidant does not decrease. Therefore, it is possible to always perform stable combustion even in the small thrust mode.
[0036]
FIG. 2 shows a second embodiment, and the same components as those of the first embodiment described above are denoted by the same reference numerals and description thereof is omitted.
[0037]
In the thruster device 1 of the present embodiment, the thrust changing member 3 is formed in a U-shape whose cross-sectional shape is open upward. The seal member 17 between the outer peripheral surface 12a of the thrust changing member 3 and the inner peripheral surface 13a of the peripheral wall 8 of the apparatus body 2 extends over the entire length of the thrust changing member 3 with the outer peripheral surface 12a and the inner peripheral surface 13a. It is arranged so as to keep the fluid tight.
[0038]
For this reason, in the thruster device 1 of the present embodiment, the thrust changing member 3 includes a cooling pipe portion 41 as a cooling path. In the illustrated example, the cooling pipe portion 41 has one end portion 41 a that opens to the branch pipe portion 24 of the fuel manifold 21 of the fuel supply means 5, and the other end portion 41 b that opens to the passage 18 in the nozzle 4. Yes.
[0039]
In the thruster device 1 configured as described above, the fuel supplied into the nozzle 4 through the branch pipe portion 24 of the fuel manifold 21 of the fuel supply means 5 through the cooling pipe portion 41 is vaporized by the heat of the nozzle 4. The nozzle 4 is cooled by the latent heat at the time of vaporization.
[0040]
Similar to the first embodiment, the thruster apparatus 1 of the present embodiment can suppress the number of parts and can always perform stable combustion even in the small thrust mode.
[0041]
Further, in the illustrated thruster apparatus 1 of the present embodiment, the cooling pipe portion 41 is open to the branch pipe portion 24 of the fuel manifold 21 of the fuel supply means 5, but the oxidant manifold 31 of the oxidant supply means 6. The cooling pipe portion 41 may be formed so as to open to the branch pipe portion 34.
[0042]
【The invention's effect】
According to the thruster device of the present invention, the large-diameter nozzle having a relatively large flow-path cross-sectional area and the small-diameter nozzle having a relatively small-diameter cross-sectional area are provided, and both the large-diameter and small-diameter nozzles are used in the injection nozzle. Between the large thrust mode for supplying the fuel and the oxidant and the small thrust mode for supplying the fuel and the oxidant into the injection nozzle using only the small-diameter nozzle.
[0043]
Therefore, by driving the thruster device in the small thrust mode, the thruster device of the present invention can be used for posture control even if the thruster for posture control in which the injection direction is arranged coaxially with the thruster device is omitted. Is possible. Therefore, the number of parts can be suppressed.
[0044]
In addition, since the thruster device uses both large and small diameter nozzles in the large thrust mode and uses only the small diameter nozzle in the small thrust mode, these fuels can be controlled even if the flow rates of the fuel and the oxidant are suppressed during attitude control. And the pressure of the oxidizing agent does not decrease. Therefore, it is possible to always perform stable combustion even in the small thrust mode.
[Brief description of the drawings]
FIG. 1 is a cross-sectional view showing a thruster device according to a first embodiment of the present invention.
2 is a cross-sectional view taken along line ii-ii in FIG.
FIG. 3 is a sectional view showing a thruster device according to a second embodiment of the invention.
FIG. 4 is a conceptual diagram showing a configuration of a conventional thruster apparatus.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 ... Thruster apparatus 2 ... Apparatus main body 3 ... Thrust changing member (Thrust changing means)
4 ... Nozzle 5 ... Fuel supply means 6 ... Oxidant supply means 17 ... Sealing member (sealing means)
25 ... Fuel large diameter nozzle (large diameter nozzle)
26 ... Fuel small diameter nozzle (small diameter nozzle)
35 ... Oxidant large diameter nozzle (large diameter nozzle)
36 ... Oxidant small diameter nozzle (small diameter nozzle)
41 ... Cooling pipe section (cooling path)

Claims (2)

A device body connected to the nozzle and forming an outer shell of the device;
Fuel supply means attached to the apparatus body and supplying fuel into the nozzle;
An oxidant supply means attached to the apparatus body and for supplying an oxidant into the nozzle;
In a thruster device comprising:
A large-diameter fuel nozzle having a relatively large cross-sectional area for guiding the fuel supplied from the fuel supply means into the nozzle;
A fuel small-diameter nozzle having a relatively small cross-sectional area of the flow path,
An oxidant large-diameter nozzle having a relatively large channel cross-sectional area for guiding the oxidant supplied from the oxidant supply means into the nozzle ;
An oxidizer small diameter nozzle having a relatively small channel cross-sectional area;
With
And a large thrust mode for guiding the fuel and the oxidant supplied from the fuel supply means and the oxidant supply means into the nozzle using the large diameter nozzle and the small diameter nozzle, and the fuel supply using only the small diameter nozzle. A thrust change member provided so as to be switchable by rotating a small thrust mode for guiding the fuel and the oxidant supplied from the means and the oxidant supply means into the nozzle, respectively, with respect to the apparatus main body ,
A drive source for rotating the thrust change member;
A thruster device comprising: The thrust changing member is formed in a U-shaped cross section,
And sealing means for preventing leakage of at least one of the fuel supplied from the fuel supply means and the oxidant supplied from the oxidant supply means from between the apparatus main body,
A cooling path that is separate from the large diameter nozzle and the small diameter nozzle and guides at least one of the fuel and the oxidant into the nozzle;
The thruster apparatus according to claim 1, further comprising:

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